3D numerical simulation of clamshell thrust reverser with flap deployed while landing

Abstract

The flow field distribution characteristic of a clamshell thrust reverser with flap deployed while landing is investigated based on Computational Fluid Dynamics (CFD) technology. The mesh was generated with unstructured tetrahedron and unstructured hexahedron meshes and S-A turbulent model in solving Reynolds averaged N-S equations is adopted. The results show, in the range of landing speed between 136.1m/s and 17.0m/s, the hot reverse exhaust flow from the clamshell thrust reverser is not re-injected into the engine inlet; and it impinges on part of the aerofoil and pylon. As landing speed decreases, the hot reverse exhaust flow spreads forward and laterally deeper, so it may be re-injected by near engine inlet if the aerofoil sweepback is large enough, which will result in inlet distortion. When landing speed decreases down to 34m/s, the hot reverse exhaust flow starts to impinge on the ground, which may wind up some dross to the inlet. At last, the reverse thrust decreases as landing speed decreases.